Characterization and control of the interactions of a partially and a fully flowing 2D generic dual-bell nozzle with the afterbody flow

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Characterization and control of the interactions of a partially and a fully flowing 2D generic dual-bell nozzle with the afterbody flow

This project investigates the physical mechanisms of passive and active flow control techniques when applied on a backward facing step. The backward facing step portrays a simplified geometry of a rocket aft section, where the main body of the rocket connects to the nozzle. This is modelled after an actual launch vehicle. The goal of the research is to gain insights into feasible ways to influence the dominant vortex structures within the shear layer in order to reduce the dynamic loads on the nozzle. Within the frame work of the passive flow control techniques, several geometric elements are integrated onto the backward facing step while their effects on the flow are analyzed with time resolved measurement techniques (time resolved PIV, muli-pulse PIV, 3D PTV, surface pressure measurements, and PSP). On the other hand, active flow control techniques such as blowing or suction are investigated in detail, in order to see whether these flow control methods yield benefits when compared to their passive counterparts. The measurements are taking place on the Transsonic Wind Tunnel Munich (TWM), while the pre-design of the various flow control devices is supported by CFD Simulations.